"An investigation of a 1/24- scale dynamically similar model of the Douglas C-124 airplane was made to determine the ditching characteristics and proper technique for ditching the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion- picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" (p. 1).

The paper presents flight measurements of the dynamic lateral stability of the D-558-II (BuAero No. 37974) research airplane. Data are presented for a range of calibrated airspeed from 167 miles per hour to 474 miles per hour.

This investigation was made to determine whether a diamond drilling program is warranted in the search for ore, and to provide basic data to guide such drilling.

Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.

Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.

"An investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds was conducted at the NACA Lewis altitude wind tunnel. This report evaluates the compressor modifications which were restricted to (1) twisting rotor blades (in place) to change blade section angles and (2) inserting new stator diaphragms with different blade angles. Such configuration changes could be incorporated quickly and easily in existing engines at overhaul depots" (p. 1).

Abstract: "Two cases are considered. In Case I, the reactor water velocity is optimized to obtain a minimum annual cost (including amortization and operating costs) for the cooling system along. The optimum velocity for a 310 megawatt reactor is calculated to be ~25 feet per second, compared to the present design value of 30 feet per second. In Case II, the velocity which will give the minimum cost of product under the assumptions of varying power and production rate is found to be in the range from ~25 to ~40 feet per second, depending on the assumptions with respect to the variation of total investment in the reactor complex with design production capacity."

Memorandum presenting a measurement of the mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a range of Reynolds numbers.

"Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number" (p. 1).

At high excitation energies, competition of proton and c-particle emission with neutron emission becomes important. For low excitation, the competition between Y-emission, neutron emission, and fission should be taken into account. To aid in the evaluation of this competition an experiment has been performed to measure the number and energy spectrum of the protons and c-particles emitted in the high energy bombardment of uranium with protons, deuterons, and c-particles.

Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.

Report presenting testing of a rocket-powered cone-cylinder body with a conical boattail to determine the jet interference effects on drag at transonic Mach numbers. If the nozzle was overexpanded, it increased boattail pressure drag at transonic Mach numbers, but an underexpanded nozzle affected boattail drag at 1.59, followed by a drag reduction.

Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.

From Introduction: "This report presents net thrusts computed for hydrogen, diborance, and hydrazine with fuel-air ratios form stoichiometric values to 0.5. Net thrusts for fuel-rich afterburning are compared with those for stoichiometric combustion of the turbojet fuel and air augmented with a 220-second specific-impulse rocket."

The following report follows the procedures to compact blends of uranium tetrafluoride and magnesium, describing how lubrication of the compact effects the outcome of the blends.

A new and rapid method for the liquid-liquid extraction of uranium and plutonium from hydrochloric acid solution is based on the use of tri(iso-octyl)amine dissolved in xylene or methylisobutylketone. Uranium and/or plutonium are separated from thorium, alkalis, alkaline earths, rare earths, zirconium, niobium, ruthenium and other elements which do not form anionic species under the conditions described. The technique may be used for either tracer or macro quantities of uranium. Several practical applications of the method for the separations chemist are proposed.

"A method of calculating the temperature of thick walls has been developed in which the time series and the response to a unit triangle variation of surface temperature concepts are used, together with essentially standard formulas for transient temperature and heat flow into thick walls. The method can be used without knowledge of the mathematical tools of its development. The method is particularly suitable for determining the wall temperature in one-dimensional thermal problems in aeronautics where there is a continuous variation of the heat-transfer coefficient and adiabatic-wall temperature" (p. 877).

The following report summarizes the results of the laboratory-scale work and pilot-plant scale work of a salt-batch composition that reduces the hydrogen pickup by uranium rods during the beta heat treatment, and the study of the influence of humidity over the salt bath on hydrogen pickup.

The following report follows an experimental study that was made on the mass transport of chromium in polythermal inconel-fluoride fuel systems, followed by the technique of adding radioactive chromium-51 to the system as either CrF3 in the salt or as elemental chromium in the solid phase.

On May 23, 1957, a visit was made by the writer to the Selas Corporation of American in Dresher, Pennsylvania. The purpose of the visit was to discuss further investigations into methods of tubesheet brazing by direct heating. Original work along these lines has been carried out at ORNL and is covered by a memo (CF-57-4-57) to W.D. Manly, dated April 16, 1957, and entitled : Investigation of Tubesheet Brazing by a Method of Direct Heating.